U.S. patent number 3,890,060 [Application Number 05/442,893] was granted by the patent office on 1975-06-17 for acoustic duct with asymmetric acoustical treatment.
This patent grant is currently assigned to General Electric Company. Invention is credited to Norman J. Lipstein.
United States Patent |
3,890,060 |
Lipstein |
June 17, 1975 |
Acoustic duct with asymmetric acoustical treatment
Abstract
Asymmetric or peripherally discontinuous acoustic linings for
absorbing sound radiating within acoustic ducts, when properly
located in the peripheral or circumferential direction, alter the
directivity of sound emitted from an end of the duct to provide
preferential enhanced suppression in a predetermined general
direction. In a jet engine fan duct, treating the upper half
produces approximately the same noise suppression on the ground as
a fully treated duct. Another application is side lobe suppression.
Two different treatments can be used providing the asymmetric
lining is the better sound absorber.
Inventors: |
Lipstein; Norman J.
(Schenectady, NY) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
23758566 |
Appl.
No.: |
05/442,893 |
Filed: |
February 15, 1974 |
Current U.S.
Class: |
415/119;
181/214 |
Current CPC
Class: |
F02K
1/827 (20130101); F04D 29/664 (20130101); B64D
2033/0286 (20130101); B64D 2033/0206 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F04D
29/66 (20060101); F02K 1/00 (20060101); F02K
1/82 (20060101); F01d 025/00 (); F01n 007/00 () |
Field of
Search: |
;181/33E,33H,33HA,33HB,33L,42,50 ;415/119 ;137/15.1 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Tomsky; Stephen J.
Assistant Examiner: Gonzales; John F.
Attorney, Agent or Firm: Campbell; Donald R. Cohen; Joseph
T. Squillaro; Jerome C.
Claims
What is claimed is:
1. An improved noise-suppressing fan duct for an aircraft jet
engine having a fan disposed within an annular fan duct air passage
comprising
a generally streamlined rigid fan duct with a circular cross
section having an asymmetric, circumferentially discontinuous
acoustic lining attached to the inner surface thereof for absorbing
noise which radiates within said duct,
said asymmetric acoustic lining being located on the upper portion
of the circumference of said duct and being effective to alter the
directivity of noise emitted from an end of said fan duct and
produce an asymmetric directivity pattern characterized by
preferential enhanced suppression of noise in an angular sector
generally below the jet engine,
wherein said asymmetric acoustic lining is approximately
semicylindrical and is continuous and uninterrupted in both the
axial and circumferential directions, and
further including a second acoustic lining attached to the lower
half of the circumference of said duct, said first-mentioned
asymmetric acoustic lining having a higher sound absorption
coefficient than said second acoustic lining.
2. An improved noise-suppressing fan duct for an aircraft jet
engine having a fan disposed within an annular fan duct air passage
comprising
a generally streamlined rigid fan duct with a circular cross
section having an asymmetric, circumferentially discontinuous
acoustic lining attached to the inner surface thereof for absorbing
noise which radiates within said duct,
said asymmetric acoustic lining being located on the upper portion
of the circumference of said duct and being effective to alter the
directivity of noise emitted from an end of said fan duct and
produce an asymmetric directivity pattern characterized by
preferential enhanced suppression of noise in an angular sector
generally below the jet engine,
wherein said asymmetric acoustic lining is made of a fibrous
acoustic material and is continuous and substantially uninterrupted
in both the axial and circumferential directions, and further
including
a second acoustic lining attached to the lower portions of the
circumference of said duct, said first-mentioned asymmetric
acoustic lining having a higher sound absorption coefficient than
said second acoustic lining.
3. An improved noise-suppressing fan duct for an aircraft jet
engine having a fan disposed within an annular fan duct air passage
comprising
a generally streamlined rigid fan duct with a circular cross
section having an asymmetric, circumferentially discontinuous
acoustic lining attached to the inner surface thereof for absorbing
noise which radiates within said duct,
said asymmetric acoustic lining being located on the upper portion
of the circumference of said duct and being effective to alter the
directivity of noise emitted from an end of said fan duct and
produce an asymmetric directivity pattern characterized by
preferential enhanced suppression of noise in an angular sector
generally below the jet engine,
wherein said asymmetric acoustic lining is made of a fibrous
acoustic material, and further including
a second acoustic lining attached to the lower portion of the
circumference of said duct, said second acoustic lining having
provision for drainage of ingested liquids and a lower sound
absorption coefficient than said first-mentioned asymmetric
acoustic lining,
said first-mentioned asymmetric acoustic lining and second acoustic
lining in combination being circumferentially continuous, each
individual lining further being continuous and substantially
uninterrupted in both the circumferential and axial directions.
4. A sound suppressing acoustic duct comprising
an axially extending, relatively rigid hard-walled duct having
attached to a portion of the periphery of the inner surface thereof
a first asymmetric sound absorbing acoustic lining, a second sound
absorbing acoustic lining attached to the remaining portion of the
periphery of the inner surface of said duct, said first and second
acoustic linings in combination being peripherally continuous and
functioning to absorb sound which radiates longitudinally through
said duct and is reflected internally,
each of said acoustic linings individually being continuous and
substantially uninterrupted in both the axial and peripheral
directions, said first acoustic lining further having a higher
sound absorption coefficient than said second acoustic lining,
said first asymmetric sound absorbing lining being peripherally
located at any desired peripheral location to alter the directivity
of sound emitted from an end of said duct and produce an asymmetric
directivity pattern characterized by preferential enhanced
suppression of sound in a preselected angular sector.
5. A sound suppressing acoustic duct according to claim 4 wherein
said duct is an aircraft jet engine fan duct and at least said
first acoustic lining is made of a fibrous acoustic material.
6. A sound suppressing acoustic duct comprising
an axially extending, relatively rigid duct having a hard-walled
inner surface into which is recessed an attached acoustic lining
for preferential side lobe suppression comprised by a pair of
opposing sound absorbing strips for absorbing sound which radiates
longitudinally through said duct and is reflected internally,
each of said sound absorbing strips being made of the same acoustic
material and each being continuous and substantially uninterrupted
in both the axial and peripheral directions.
said pair of opposing sound absorbing strips being peripherally
spaced from one another and peripherally located and dimensioned to
obtain preferential enhanced side lobe suppression of the sound
emitted from an end of said duct.
Description
BACKGROUND OF THE INVENTION
This invention relates to sound-absorbing acoustic ducts, and more
particularly to an acoustic duct with asymmetric or peripherally
discontinuous acoustical treatment. As a typical application, the
invention relates to an asymmetric noise suppressing acoustic
lining for the inlet of an aircraft jet engine fan.
Sound-absorbing acoustical material used as a lining in acoustic
ducts is ordinarily applied symmetrically in the axial or
longitudinal direction. That is, the acoustical material is
circumferentially or peripherally continuous at any given axial or
longitudinal location. By way of example, the sound absorbing
linings at the inlet air passage of a jet engine fan in an airplane
are applied over a full 360.degree. of the internal surface of the
fan cowling or casing. This is illustrated in U.S. Pat. No.
3,542,152 to A. P. Adamson, G. D. Oxx, Jr., and W. R. Morgan,
assigned to the same assignee as this invention, in which the
acoustical material is a honeycomb-type panel with tuned resonant
cavity structures for the absorption of broadband noise. Provision
is made for drainage of ingested liquid both in the sound-absorbing
panel itself and in the cowling. Although advantageous for this
application, the improved asymmetric acoustical treatment technique
has utility in numerous other applications such as silencers for
industrial gas turbines, and modifying the directivity patterns of
acoustical horns.
SUMMARY OF THE INVENTION
It has been found that an asymmetric or peripherally discontinuous
acoustic lining for absorbing sound radiating within an acoustic
duct, depending upon its location and extent in the peripheral
direction, has the capability of selectively altering the
directivity of sound emitted from an end of the duct. The altered
directivity of radiated sound or noise is employed to provide
preferential enhanced suppression of sound in a preselected angular
sector of the directivity pattern. In the preferred embodiment, fan
noise produced in an aircraft jet engine fan duct is selectively
suppressed in the sector generally beneath the fan duct inlet by
treating only the upper portion of the inner surface of the duct. A
fibrous acoustic material with a higher sound absorption
coefficient can be used, and for a 180.degree. semicylindrical
acoustic lining, for example, the amount of noise suppression as to
a ground observer is approximately the same as for the full
360.degree. treatment. The advantage is thus a reduction of
required acoustic material or weight, or conversely an increased
effect for the same amount of treatment. It is believed that the
theoretical explanation relates to the better reflection of sound
by the untreated lower inner surface of the rigid or hard-walled
duct.
As a modification of the invention, a second acoustic lining is
used to treat all or a portion of the remaining inner surface of
the fan or other acoustic duct. To obtain an asymmetrical
directivity pattern, the first-mentioned asymmetric lining has a
higher sound absorption coefficient than the second lining. Another
embodiment is an asymmetrically treated acoustical duct for side
lobe suppression, which includes an acoustic lining with a pair of
opposing sound-absorbing strips, each of which effects selective
suppression of the opposite side lobe in the directivity pattern.
These are illustrative of the many variations of the asymmetric
placement of acoustic material in acoustic ducts for a desired
preferential effect, and of the variety of possible
applications.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a diagrammatic side elevational view, partially in
longitudinal cross section, of the forward portion of a ducted fan
type aircraft jet engine having a fan duct provided with an
asymmetric semicylindrical acoustic lining according to the
teaching of the invention;
FIG. 2 is a vertical cross-sectional view of only the inlet fan
duct or casing taken on the line 2--2 of FIG. 1 and showing the
180.degree. asymmetric acoustical treatment for preferential noise
suppression as to a ground observer;
FIG. 3 shows three typical experimentally obtained directivity
patterns for a cylindrical jet engine fan duct for the cases when
the duct is untreated, has 360.degree. acoustical treatment, and
has a 180.degree. acoustical treatment;
FIG. 4 is a cross section similar to FIG. 2 illustrating another
aspect of the invention using two different acoustic lining
materials for optimum economic and noise suppression effect;
and
FIG. 5 is a cross section through an acoustic duct with asymmetric
treatment for side lobe suppression.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Although the invention has general applicability to acoustic ducts
used for noise and sound suppression, the application discussed in
detail with regard to FIGS. 1-4 is an asymmetric or
circumferentially discontinuous acoustic lining for the inlet duct
of an aircraft jet engine fan to reduce the noise level heard at
the ground during take-off and landing. In FIG. 1, there is shown
generally at 10 a ducted fan type turbojet engine having an annular
streamlined fan duct air passage 11 formed by an annular cowling or
fan casing 12 of streamlined cross section and a suitable engine
nacelle structure 13 projecting within the cowling 12. The nacelle
structure 13, of which only the forward portion is shown here in
outline, houses a suitable compressor, combustor, and
turbomachinery for, as part of its functions, driving a fan 14
disposed in the air passage 11 between the forward end of the
cowling 12 and the nacelle structure 13. The fan 14 drives inlet
air axially through the primary air passage 11 to provide
propulsive thrust to the engine as well as to supply air to the
compressor through a second, inner air passage 15. The major part
of the fan flow exits through an annular exhaust nozzle opening 16
formed by the inner surface of the cowling 12 and the outer surface
of a gas generator pod casing 17. The compressor inlet air passage
15 is formed between the inner casing 17 and the forwardly
projecting, tear-shaped, fan mounting and drive structure 18. The
outer surface of casing 17 is suitably lined with the honeycombed,
resonant chamber sound-absorbing panels 19 previously discussed.
For further information on this type of turbofan jet engine,
reference may be made to U.S. Pat. No. 3,540,682 to C. G. Dibble
and D. F. Howard, assigned to the same assignee as this
invention.
As best shown in FIG. 2, the inside surface of the cowling 12 has
an attached, asymmetrical semicylindrical acoustic lining 20 which,
in this embodiment of the invention, covers only the top half of
the inner surface. This structure will hereafter be referred to as
an asymmetrically treated fan duct. By using the 180.degree.
sound-absorbing acoustical treatment on the upper half of the fan
duct, the suppression of noise as to a ground observer is almost
the same, or approximately the same, as if the prior known
360.degree. acoustical treatment were used. To further explain
this, the directivity of noise emitted by the fan 14 is altered
such that there is preferential or enhanced suppression of the
noise pressure level in a selected direction, in this case
generally beneath the noise source. The fan 14 produces broadband
noise, and is the major source of jet engine noise. A variety of
acoustic lining materials can be used, including the honeycombed,
resonant chamber sound-absorbing panels shown in the previously
mentioned U.S. Pat. No. 3,542,152, but it is preferred to employ a
fibrous acoustic material with a higher sound absorption
coefficient. Since the acoustic lining 20 covers only the top half
of the fan duct, the need to use a material which provides for
drainage of ingested liquids is diminished if not substantially
eliminated. Among the suitable fibrous acoustic materials are
fiberglass, stainless steel wool, and mineral wool for high
temperature portions of the duct. The advantage of the 50 percent
or asymmetrically treated fan duct is evident, since practically
the same noise suppression effect is obtained with only half the
cost and weight as the previously full 360.degree. treatment. In
addition to minimizing the treatment weight, the cost per square
foot of the above and other fibrous acoustic materials may be less
than that of the honeycombed, resonant chamber sound-absorbing
panels. Alternatively, for the same treatment weight there is an
increased noise suppression effect. Further, there may be lower air
flow losses in the fan duct due to the improved flow over the
smooth, untreated duct surfaces.
The altered, asymmetric directivity pattern of noise radiating from
the inlet end of a semicylindrically, 50 percent treated fan duct
is shown in FIG. 3. The upper half of the experimental fan duct 21
is the acoustically treated semicylinder, while the bottom half is
the untreated semicylinder. Measurements were made in an anechoic
chamber using a one-third scale model of the General Electric CF6
jet engine fan run at 90 percent design speed. To provide a basis
for comparison, the symmetrical directivity patterns for an
untreated fan duct and a 360.degree. fully treated fan duct using
the same acoustic material are illustrated respectively in dashed
and dotted lines. Immediately beneath the duct inlet, the reduction
in sound pressure level produced by the full acoustical treatment
is about 8 decibels. The asymmetrical directivity pattern obtained
by using the new 180.degree. treatment is shown in full lines. It
will be observed that over a large angular sector generally beneath
and in front of the duct inlet, the amount of noise suppression
using the 180.degree. treatment is approximately the same as for
the full 360.degree. treatment. For the data taken, the noise
reduction with the 180.degree. treatment as compared to full
treatment is almost the same over the sector from 50.degree. to
110.degree. measured downwardly with reference to the forwardly
projected duct axis. The noise suppression effect immediately in
front of the duct inlet is not as favorable as that obtained by use
of the full treatment, but there is less concern about noise
suppression in these spatial regions since the primary objective of
the acoustical treatment is the reduction of noise heard by human
beings at ground level. Immediately above the duct inlet the noise
suppression effect of the treatment is about half that of the full
360.degree. treatment. The redirection of noise obtained by use of
the asymmetrical acoustical treatment, shown here for an
axisymmetrical noise source, is independent of the type of acoustic
material employed, and it is understood that the circumferential
location of the asymmetric treatment determines the general
direction at which the preferential noise suppression is obtained.
Thus, for the case of reducing fan noise for another application,
when the bottom half of the fan duct is treated rather than the top
half, the preferential, enhanced noise suppression is obtained
above the duct inlet rather than below.
Although the theoretical explanation for the altered directivity of
sound radiating from an asymmetrically treated fan duct or other
acoustic duct is not known with certainty, it is believed it can be
explained in terms of the reflection of sound by the internal
surfaces of the duct. Broadband noise emitted by the
axisymmetrically located fan radiates in all directions, and some
of the sound waves are incident upon the treated semicylindrical
duct surface, others are incident upon the untreated
semicylindrical surface, and a portion radiates directly out the
end of the fan duct. Sound striking the treated upper half is
partially absorbed and partially reflected, while that incident on
the untreated lower half of the duct, which is lined with smooth
sheet metal panels, is almost totally reflected. Some of the sound
reflected off the untreated lower half is, in turn, incident upon
the treated upper half where it is partially absorbed. Conversely,
some of the sound reflected from the treated upper half is radiated
toward the lower half, where it is again reflected to the
sound-absorbing upper half. Eventually, the unabsorbed sound energy
radiates out the duct inlet, but it is readily seen that the higher
sound pressure level energy reflected from the untreated lower half
adjacent the duct inlet radiates in a generally upward direction,
while the reduced sound pressure level energy reflected from the
treated upper half and out the duct inlet radiates in a generally
downward direction. Thus, the directivity pattern is asymmetrical,
with the preferential or enhanced noise suppression being
determined by the circumferential placement of the acoustic
material. These results are generally applicable to arcuate
asymmetric treatments with an angular extent greater or less than
180.degree., the limits being determined at either side by
practical considerations and the intended application, weighing the
cost of the acoustic material versus the amount of preferential
noise suppression desired. Moreover, the invention is applicable in
general to acoustic ducts with cross sections other than circular,
such as rectangular and square.
Referring to FIG. 4, a modification is the use of two different
acoustic lining materials for optimum noise suppression effect.
This is particularly well illustrated in the case of the fan duct
for the aircraft jet engine. According to the modification, the
upper half of the inner surface of the cowling 12 is lined with the
fibrous acoustic material 20, while the lower half is lined with
the previously mentioned honeycombed, resonant chamber
sound-absorbing structural panel material 22. The first acoustic
treatment material 22 has the advantage of durability and good
drainage for ingested liquids, while the second acoustical
treatment material 20 is desirably selected to obtain the
combination of lower cost with a higher sound absorption
coefficient. The structural acoustic panels 22 are made of, or have
a facing sheet made of, a rigid material such as a suitable metal
or plastic, and reflect sound more readily than the fibrous
acoustic material 20. By the full treatment of the fan duct in this
manner the directivity pattern as a whole is improved with good
noise reduction above and forward of the duct inlet, while still
retaining the enhanced noise reduction generally below the duct
inlet due to the use of the better sound-absorbing material on the
upper half of the duct. Instead of being circumferentially
continuous as illustrated, there can be a gap between the two
different acoustical treatments.
Another embodiment of the invention shown in FIG. 5 illustrates the
applicability of the principle of asymmetric acoustical treatment
to the suppression of side lobes. The duct 23 in this case is a
hard-walled acoustical duct suitable for other applications such as
a silencer for an industrial gas turbine, or in an acoustical horn
structure. In the gas turbine silencer application, to explain the
principle, it may be desirable to direct the noise away from
residential areas. In this case, two diametrically opposing arcuate
strips 24a and 24b of the same acoustic material are used. It is
understood that the duct 23 has a length at least equal to or
greater than the diameter and that the sound-absorbing strips 24a
and 24b extend axially throughout the length of the duct or a
specified portion of the length. Assuming a noise source that would
produce symmetrical directivity patterns with side lobes, the
effect of the asymmetric left-hand acoustic treatment 24a is to
suppress the side lobe at the right-hand side of the directivity
pattern, while conversely the effect of the asymmetric right-hand
acoustic treatment 24b is to suppress the side lobe at the
left-hand side of the directivity pattern. The explanation for the
resulting altered directivity pattern, with preferential noise
suppression at both sides, is similar to that for the fan duct
application and need not be repeated. The required arcuate extent
of the acoustic material strips 24a and 24b to produce side lobe
suppression can be determined easily. As in the fan duct case (see
FIG. 4), over-all noise reduction is improved by the use of two
different acoustic materials, with the understanding that the side
lobe suppression strips 24a and 24b are made of a material with a
higher sound absorption coefficient.
In summary, asymmetric acoustic linings for suppressing sound and
noise emitted from acoustic ducts, when properly located in the
peripheral or circumferential direction, have the advantage of
minimizing the amount of acoustic material needed for a desired
result, or conversely achieve an increased effect with the same
amount of treatment. The reduction of jet engine fan noise on the
ground, and acoustic ducts for side lobe suppression have been
discussed, but many other applications are possible.
While the invention has been particularly shown and described with
reference to several preferred embodiments thereof, it will be
understood by those skilled in the art that various changes in form
and details may be made therein without departing from the spirit
and scope of the invention.
* * * * *